CN109696308B - Aviation actuator loading test device under vibration environment and loading method thereof - Google Patents
Aviation actuator loading test device under vibration environment and loading method thereof Download PDFInfo
- Publication number
- CN109696308B CN109696308B CN201910167580.6A CN201910167580A CN109696308B CN 109696308 B CN109696308 B CN 109696308B CN 201910167580 A CN201910167580 A CN 201910167580A CN 109696308 B CN109696308 B CN 109696308B
- Authority
- CN
- China
- Prior art keywords
- loading
- valve
- hydraulic cylinder
- actuator
- hydraulic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/16—Servomotor systems without provision for follow-up action; Circuits therefor with two or more servomotors
- F15B11/17—Servomotor systems without provision for follow-up action; Circuits therefor with two or more servomotors using two or more pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
- F15B13/06—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with two or more servomotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B21/00—Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
- F15B21/08—Servomotor systems incorporating electrically operated control means
- F15B21/087—Control strategy, e.g. with block diagram
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0042—Pneumatic or hydraulic means
- G01N2203/0048—Hydraulic means
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Analytical Chemistry (AREA)
- Chemical & Material Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Health & Medical Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Fluid Mechanics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application discloses an aviation actuator loading test device under a vibration environment, which comprises a first reaction frame, a first connecting rod, an environment test box, a second connecting rod, a second reaction frame, a low-pass loading device, a second sliding table, a force sensor, a vibration table and a first sliding table, wherein a tested actuator is arranged on the vibration table and is positioned in the environment test box, the rod end of the tested actuator is connected with a hydraulic cylinder of the low-pass loading device through the second connecting rod and a crank of the second reaction frame, the tail part of the tested actuator is connected with the first reaction frame through the first connecting rod, the force sensor is arranged between the rod end of the tested actuator and the second connecting rod, the sliding table is arranged between the tested actuator and the vibration table, when the low-pass loading device works, a motor and a hydraulic pump are always in an operating state, the oil pressure is controlled through a reverse proportion overflow valve, and the loading force direction is controlled by two high-speed switch valves. The application solves the problem of coupling of vibration stress and loading force, and eliminates the influence of high-frequency vibration on loading precision.
Description
Technical Field
The application belongs to the field of mechanical equipment reliability and life test, and particularly relates to an aeronautical actuator loading test device and a loading method thereof under a vibration environment.
Background
The aviation actuator is used as a complex product with high integration of mechanical, electric, hydraulic and magnetic, and the functions and performances of the aviation actuator are comprehensively influenced by electromagnetic fields, flow fields, thermal fields, stress, friction, creep and other physical fields and multiple factors. In the working process of the aviation actuator, the aviation actuator is subjected to the vibration environment of 20 Hz-2000 Hz and is also influenced by various load forces, so that faults such as cracks, leakage, clamping stagnation and the like of products are induced, and the service life is greatly reduced. Therefore, a proper test device and a correct test method are selected in the loading test process of the aviation actuator under the vibration environment, so that the accuracy and the effectiveness of a test result are important, and effective data support can be provided for the design improvement of the aviation actuator.
When the working load is constant, the prior art adopts a mass block, a friction disc and a spring loading mode, and the loading mechanism and the tested actuator are simultaneously placed in a vibration environment, so that the two systems cannot relatively move due to vibration, loading under the condition of comprehensive stress can be realized, the test method is simple, and the implementation difficulty is low; the test chamber at the upper part of the test platform can be divided into two parts, wherein one part is provided with a high-temperature chamber and a low-temperature chamber for mounting test pieces, the other part is provided with a normal-temperature chamber for mounting loading elements, and the loading part and the test part are connected with the vibration platform through a transition tooling plate and vibrate together. Although the method can effectively avoid the coupling problem of vibration and loading force, the actual situation is that the loading system and the tested actuator are simultaneously placed in a vibration environment, the loading system is extremely easy to damage, the loading precision is affected, and great equipment maintenance cost is brought.
Disclosure of Invention
Aiming at the situation, the application provides an aero-actuator loading test device in a vibration environment, overcomes the defects of the prior art, can effectively shield disturbance of a tested actuator on loading force, and is widely used for loading tests of aero-actuators in the vibration environment.
The technical scheme adopted by the application is to provide an aviation actuator loading test device under a vibration environment, which comprises a first reaction frame, a first connecting rod, an environment test box, a second connecting rod, a second reaction frame, a low-pass loading device, a second sliding table, a force sensor, a vibrating table and a first sliding table, wherein the low-pass loading device comprises a loading hydraulic cylinder, a first one-way valve, a second one-way valve, a third one-way valve, a first high-speed switch valve, a second high-speed switch valve, a pressure oil tank, a second motor, a second hydraulic pump, a voltage stabilizer and an electrohydraulic inverse proportion overflow valve, the second motor is connected with the second hydraulic pump, an oil inlet of the second hydraulic pump is connected with the pressure oil tank, the first one-way valve is connected between an oil outlet of the second hydraulic pump and a first oil port of the loading hydraulic cylinder, the first one-way valve is in one-way conduction from the second hydraulic pump to the first oil port, the first high-speed switch valve is connected to a pipeline between a third oil port and a fourth oil port of the loading hydraulic cylinder, the second high-speed switch valve is connected to a pipeline between the fourth oil port and a pressure oil tank of the loading hydraulic cylinder, the second one-way valve is arranged on a piston of the loading hydraulic cylinder, the second one-way valve is in one-way conduction from a rodless cavity to a rod cavity of the loading hydraulic cylinder, the third one-way valve is connected between a fifth oil port and the pressure oil tank of the loading hydraulic cylinder, the third one-way valve is in one-way conduction from the pressure oil tank to the fifth oil port, the electro-hydraulic inverse proportion overflow valve is connected between the pressure oil tank and the second oil port of the loading hydraulic cylinder, the pipeline between the electro-hydraulic inverse proportion overflow valve and the loading hydraulic cylinder is connected with a control oil way of the electro-hydraulic inverse proportion overflow valve, and is connected in parallel with the voltage stabilizer.
The device comprises a vibration table, a tested actuator, a force sensor, a first sliding table, a second sliding table, a first counter-force frame, a second counter-force frame, a first connecting rod, a second connecting rod, a first sliding table and a second sliding table, wherein the tested actuator is arranged on the table top of the vibration table and in an environment test box; the servo valve is connected to a pipeline between the tested actuator and the first hydraulic pump, an oil inlet of the first hydraulic pump is connected with the oil tank, an oil return pipeline of the servo valve is connected with the oil tank, the first hydraulic pump is connected with the first motor, the servo valve is connected with the control system through a servo valve driving signal channel, a displacement sensor is arranged between the surface, in contact with the vibrating table, of the second end of the tested actuator, the displacement sensor feeds back a displacement feedback signal to the control system, the force sensor feeds back a force feedback signal to the control system, the electro-hydraulic inverse proportion overflow valve feeds back an overflow valve pressure control signal to the control system, the second motor feeds back a hydraulic pump motor driving signal to the control system, and the first high-speed switch valve and the second high-speed switch valve feed back a first high-speed switch valve switching signal and a second high-speed switch valve switching signal to the control system respectively.
Preferably, the low-pass loading means takes as output a loading force.
Preferably, the tested actuator loading control system controls the tested actuator in a displacement control mode to reciprocate at a frequency of less than 5 Hz.
Further, the loading hydraulic cylinder adopts a single-rod asymmetric hydraulic cylinder, and the piston size of the loading hydraulic cylinder meets the formula D 2 -d 2 ＝d 2 Wherein D represents the major diameter of the piston and D represents the diameter of the piston rod.
Preferably, the hydraulic pump employs a metered hydraulic pump having a nominal flow rate of greater than 60L/min.
Preferably, the proportional overflow valve is an electro-hydraulic inverse proportional overflow valve, the rated flow of the electro-hydraulic inverse proportional overflow valve is larger than 60L/min, and the response frequency is smaller than 30Hz.
Preferably, the first high-speed switch valve and the second high-speed switch valve have two states of on and off when working, the first high-speed switch valve is respectively communicated with the rodless cavity and the rod-containing cavity of the loading hydraulic cylinder, and the second high-speed switch valve is respectively communicated with the rodless cavity of the loading hydraulic cylinder and the pressure oil tank, and the response speed of the second high-speed switch valve is less than 3ms.
The application also provides a loading method for loading the test device by using the aviation actuator under the vibration environment, which comprises the following steps:
s1: the second motor and the second hydraulic pump always keep an operating state, and constant oil flow is provided for a rod cavity of the loading hydraulic cylinder;
s2: when the piston rod of the loading hydraulic cylinder stretches out, the loading hydraulic cylinder stretches out leftwards under the drive of the tested actuator, and the loading force direction is rightwards;
s3: the first high-speed switch valve Guan Faguan and the second high-speed switch valve are opened, and a rodless cavity of the loading hydraulic cylinder and a pressure oil tank are communicated;
s4: the loading hydraulic cylinder moves leftwards, and oil in the rod cavity flows back to the pressure oil tank through the electro-hydraulic inverse proportion overflow valve;
s5: the pressure oil tank supplements oil to the rodless cavity through the first one-way valve and the second high-speed switch valve;
s6: the control system calculates a theoretical output force instruction according to the signal of the displacement sensor, compares the theoretical output force instruction with the signal of the force sensor, sends a control signal to the electro-hydraulic inverse proportion overflow valve, controls the pressure of a rod cavity of the loading hydraulic cylinder, and realizes the extension of a piston rod;
s7: when the piston rod of the loading hydraulic cylinder is retracted, the loading hydraulic cylinder is retracted rightwards under the drive of the tested actuator, and the direction of loading force is leftwards;
s8: the first high-speed switch valve is opened, a rod cavity and a rodless cavity of the loading hydraulic cylinder are communicated, and the second high-speed switch valve is closed;
s9: the loading hydraulic cylinder moves rightwards, and the oil in the rodless cavity supplements oil to the rod-containing cavity through the first high-speed switch valve and the second one-way valve;
s10: the redundant oil in the rod cavity flows back to the pressure oil tank through the electro-hydraulic inverse proportion overflow valve; and
s11: the control system calculates a theoretical output force command according to the signal of the displacement sensor, compares the theoretical output force command with the signal of the force sensor, sends a control signal to the electro-hydraulic inverse proportion overflow valve, controls the pressure of the rod cavity of the loading hydraulic cylinder, and realizes the retraction of the piston rod.
Compared with the prior art, the application has the following advantages:
1. the problem of coupling of vibration stress and loading force is solved, and the purpose of loading test under the vibration environment of the aviation actuator is achieved;
2. the low-pass filtering loading device utilizing the pressure control characteristic of the electro-hydraulic inverse proportion overflow valve eliminates the influence of high-frequency vibration on loading precision;
3. the problems of coupling of the overturning moment caused by the loading lateral force, the radial force caused by the vertical vibration and the displacement caused by the horizontal vibration with the loading force are solved.
Drawings
FIG. 1 is a schematic view of the overall structure of the device of the present application;
fig. 2 is a schematic structural diagram of the working principle of the control system of the present application.
Detailed Description
In order to make the technical content, the structural features, the achieved objects and the effects of the present application more detailed, the following description will be taken in conjunction with the accompanying drawings.
The application provides an aviation actuator loading test device under a vibration environment, as shown in figures 1 and 2, the device comprises a first counter-force frame 31, a first connecting rod 30, an environment test box 1, a tested actuator 4, a second connecting rod 32, a second counter-force frame 33, a low-pass loading device 34, a second sliding table 36, a force sensor 9, a vibration table 28 and a first sliding table 35, wherein the low-pass loading device 34 comprises a loading hydraulic cylinder 15, a first check valve 20, a second check valve 18, a third check valve 16, a first high-speed switching valve 11, a second high-speed switching valve 12, a pressure oil tank 17, a second motor 19, a second hydraulic pump 21, a pressure stabilizer 22 and an electrohydraulic counter-proportion relief valve 23, the second motor 19 is connected with the second hydraulic pump 21, an oil inlet of the second hydraulic pump 21 is connected with the pressure oil tank 17, an oil outlet is connected with a first end of the first check valve 20, a second end of the first check valve 20 is connected with a first oil port of the loading hydraulic cylinder 15, the first check valve 20 is in one-way conducted from the second hydraulic pump 21 to the first oil port, the first high-speed switching valve 11 is connected with the third hydraulic cylinder 15, a hydraulic cylinder 17 is connected with the third hydraulic cylinder 17 and a hydraulic cylinder 17 is connected with the hydraulic cylinder 17 in one-way through a fifth hydraulic valve 17, the hydraulic valve is connected with the hydraulic cylinder 17 through a fifth hydraulic valve 17, the hydraulic valve 17 is connected with the hydraulic cylinder 17 through a hydraulic valve 17, the hydraulic valve is connected with the hydraulic valve 17 through a fifth hydraulic valve is connected with the hydraulic cylinder 17 through a hydraulic valve 17, the hydraulic valve is connected with the hydraulic valve 17 through the hydraulic cylinder through the fourth port is connected with the hydraulic valve 17 through the hydraulic valve 17 and the hydraulic tank 17 through the hydraulic tank has the valve with the hydraulic tank 17, and the pipeline between the electro-hydraulic inverse proportion overflow valve 23 and the loading hydraulic cylinder 15 is connected with a control oil way of the electro-hydraulic inverse proportion overflow valve 23 and is connected with the voltage stabilizer 22 in parallel; the tested actuator 4 is placed on the table top of the vibration table 28 and is placed in the environment test box 1, the environment test box 1 is fixedly connected with the vibration table 28, the first end of the tested actuator 4 is connected with the knuckle bearing 10 at the front end of a piston rod of a loading hydraulic cylinder 15 of a low-pass loading device 34 through a second connecting rod 32 and a crank of a second counter-force frame 33, the second end of a cylinder barrel of the tested actuator 4 is connected with the first counter-force frame 31 through a first connecting rod 30, the force sensor 9 is placed between the first end of the tested actuator 4 and the second connecting rod 32, a first sliding table 35 and a second sliding table 36 are designed between the tested actuator 4 and the vibration table 28, when the vibration table 28 vibrates horizontally, loading counter-force is provided by the vibration table 28, and at the moment, the first connecting rod 30, the first sliding table 35 and the second sliding table 36 are not needed; and the servo valve 5 is connected to a pipeline between the tested actuator 4 and the first hydraulic pump 6, an oil inlet of the first hydraulic pump 6 is connected with the oil tank 7, an oil return pipeline of the servo valve 5 is connected with the oil tank 7, the first hydraulic pump 6 is connected with the first motor 8, the servo valve 5 is connected with the control system 27 through a servo valve driving signal channel 3, a displacement sensor 2 is arranged between the surface, which is contacted with the vibration table 28, of the second end of the tested actuator 4, the displacement sensor 2 feeds back a displacement feedback signal 29 to the control system 27, the force sensor 9 feeds back a force feedback signal 26 to the control system 27, the electro-hydraulic inverse proportion overflow valve 23 feeds back an overflow valve pressure control signal 25 to the control system 27, the second motor 19 feeds back a hydraulic pump motor driving signal 24 to the control system 27, and the first high-speed switch valve 11 and the second high-speed switch valve 12 feed back a first high-speed switch valve switching signal 13 and a second high-speed switch valve switching signal 14 to the control system 27 respectively.
The low-pass loading device 34 takes as output a loading force. The load control system of the tested actuator 4 controls the tested actuator 4 in a displacement control mode, and controls the tested actuator 4 to reciprocate at a frequency not higher than 5 Hz. The loading hydraulic cylinder 15 adopts a single-rod asymmetric hydraulic cylinder, and the size of the piston of the hydraulic cylinder meets the formula D 2 -d 2 ＝d 2 Wherein D represents a pistonWhen the piston rod of the loading hydraulic cylinder stretches out or retracts, the loading hydraulic cylinder can stretch out or retract rightwards better under the drive of the tested actuator, and the output force is basically consistent when the two directions of movement are realized.
The first hydraulic pump 6 and the second hydraulic pump 21 are fixed-displacement hydraulic pumps, and the rated flow rate of the fixed-displacement hydraulic pumps is larger than 60L/min. The proportional overflow valve is an electro-hydraulic inverse proportional overflow valve 23, the rated flow of the electro-hydraulic inverse proportional overflow valve is not less than 60L/min, and the response frequency is not more than 30Hz. The first high-speed switch valve 11 and the second high-speed switch valve 12 only have two states of on and off when working, the first high-speed switch valve 11 is communicated with the rodless cavity and the rod-containing cavity of the loading hydraulic cylinder 15, and the second high-speed switch valve 12 is communicated with the rodless cavity and the pressure oil tank of the loading hydraulic cylinder 15, and the response speed is less than 3ms.
The tested actuator 4 is mounted in the environment test chamber 1 for simulating an external temperature environment and mounted on the vibration table 28 for simulating an external vibration environment. The control system 27 sends a control signal to the servo valve 5 according to the signal of the displacement sensor 2, controls the tested actuator to reciprocate at a frequency not higher than 5Hz, and the first hydraulic pump 6, the oil tank 7 and the first motor 8 are used for providing hydraulic oil to the tested actuator 4. The loading hydraulic cylinder 15 is connected with the tested actuator 4 through the knuckle bearing 10, and loads in a follow-up loading mode.
When the piston rod of the loading hydraulic cylinder 15 extends out, the loading method of the loading test device of the aviation actuator in the vibration environment comprises the following steps:
s1: the second motor 19 and the second hydraulic pump 21 are kept in an operating state all the time, and constant oil flow is provided for the rod cavity of the loading hydraulic cylinder 15;
s2: the loading hydraulic cylinder 15 stretches out leftwards under the drive of the tested actuator 4, and the direction of loading force is rightwards;
s3: the first high-speed switch valve 11 is in a closed state, the second high-speed switch valve 12 is in an open state, and a rodless cavity of the loading hydraulic cylinder 15 is communicated with the pressure oil tank 17;
s4: the loading hydraulic cylinder 15 moves leftwards, and oil in a rod cavity flows back to the pressure oil tank 17 through the electro-hydraulic inverse proportion overflow valve 23;
s5: the pressure oil tank 17 supplements oil to the rodless cavity through the first check valve 20 and the second high-speed switch valve 12;
s6: the control system 27 calculates a theoretical output force command according to the signal of the displacement sensor 2, compares the theoretical output force command with the signal of the force sensor 9, sends a control signal to the electro-hydraulic inverse proportion overflow valve 23, controls the pressure of the rod cavity of the loading hydraulic cylinder 15, and the pressure stabilizer 22 is used for relieving pressure fluctuation, so that the loading force is controlled, and the loading control is realized.
When the piston rod of the loading hydraulic cylinder 15 is retracted, the loading method of the loading test device of the aviation actuator in the vibration environment comprises the following steps:
s1: the second motor 19 and the second hydraulic pump 21 are kept in an operating state all the time, and constant oil flow is provided for the rod cavity of the loading hydraulic cylinder 15;
s2: the loading hydraulic cylinder 15 is driven by the tested actuator 4 to retract rightwards, and the direction of loading force is leftwards;
s3: the first high-speed switch valve 11 is switched to an open state, a rod cavity and a rodless cavity of the loading hydraulic cylinder 15 are communicated, and the second high-speed switch valve 12 is switched to a closed state;
s4: the loading hydraulic cylinder 15 moves rightwards, and the oil in the rodless cavity is supplemented to the rod cavity through the first high-speed switch valve 11 and the second one-way valve 18;
s5: because the area of the rodless cavity is larger than that of the rod cavity, redundant oil in the rod cavity flows back to the pressure oil tank 17 through the electro-hydraulic inverse proportion overflow valve 23;
s6: the control system 27 calculates a theoretical output force command according to the signal of the displacement sensor 2, compares the theoretical output force command with the signal of the force sensor 9, sends a control signal to the electro-hydraulic inverse proportion overflow valve 23, controls the pressure of the rod cavity of the loading hydraulic cylinder 15, and the pressure stabilizer 22 is used for relieving pressure fluctuation, so that the loading force is controlled, and the loading control is realized. Furthermore, in one operation, it is generally necessary to control both the extension of the piston rod of the loading cylinder 15 and the retraction of the piston rod of the loading cylinder 15, so that the two control processes are one integral unit.
The second motor 19 and the second hydraulic pump 21 mainly provide a constant oil flow to the rod cavity of the loading hydraulic cylinder 15, so that the movement speed is 0 when the loading hydraulic cylinder 15 commutates, and the electro-hydraulic inverse proportion overflow valve 23 still has a certain oil flow to pass through. This can avoid the problem of large pressure fluctuation of the electro-hydraulic inverse proportion overflow valve 23 caused by unstable pressure-flow characteristic when the flow rate is zero or very small.
In the loading process, the disturbance generated by the low-frequency motion of the tested actuator 4 is controlled through the pressure control of the electro-hydraulic inverse proportion overflow valve 23, and the high-frequency disturbance generated by the vibration table 28 is not controlled, but the attenuation of the high-frequency disturbance is realized by the structural characteristic of the electro-hydraulic inverse proportion overflow valve 23. Through reasonable system structure and parameters, the influence of high-frequency disturbance on loading force can be restrained within a certain precision range.
The foregoing description of the preferred embodiments of the present application is not intended to limit the scope of the application, and it should be noted that modifications and variations could be made by persons skilled in the art without departing from the principles of the present application, and these modifications and variations should also be regarded as being within the scope of the application.
Claims (6)
1. The loading test device of the aviation actuator in the vibration environment is characterized by comprising a first reaction frame, a first connecting rod, an environment test box, a second connecting rod, a second reaction frame, a low-pass loading device, a second sliding table, a force sensor, a vibration table and a first sliding table,
the low-pass loading device comprises a loading hydraulic cylinder, a first one-way valve, a second one-way valve, a third one-way valve, a first high-speed switching valve, a second high-speed switching valve, a pressure oil tank, a second motor, a second hydraulic pump, a voltage stabilizer and an electrohydraulic inverse proportion overflow valve, wherein the second motor is connected with the second hydraulic pump;
the tested actuator is placed on the table top of the vibrating table and is placed in an environment test box, the environment test box is fixedly connected with the vibrating table, a first end of the tested actuator is connected with a joint bearing at the front end of a piston rod of a loading hydraulic cylinder of the low-pass loading device through a second connecting rod and a crank of a second counter-force frame, a second end of a cylinder barrel of the tested actuator is connected with the first counter-force frame through the first connecting rod, the force sensor is placed between the first end of the tested actuator and the second connecting rod, and a first sliding table and a second sliding table are arranged between the tested actuator and the vibrating table;
the servo valve is connected to a pipeline between the tested actuator and the first hydraulic pump, an oil inlet of the first hydraulic pump is connected with the pressure oil tank, an oil return pipeline of the servo valve is connected with the pressure oil tank, the first hydraulic pump is connected with the first motor, the servo valve is connected with the control system through a servo valve driving signal channel, a displacement sensor is arranged between the surface, which is contacted with the vibration table, of the second end of the tested actuator, the displacement sensor feeds back a displacement feedback signal to the control system, the force sensor feeds back a force feedback signal to the control system, the electro-hydraulic inverse proportion overflow valve feeds back an overflow valve pressure control signal to the control system, the second motor feeds back a hydraulic pump motor driving signal to the control system, and the first high-speed switch valve switching signal and the second high-speed switch valve switching signal are fed back to the control system respectively;
the tested actuator loading control system controls the tested actuator in a displacement control mode to reciprocate at a frequency less than 5 Hz;
the loading hydraulic cylinder adopts a single-rod asymmetric hydraulic cylinder, and the size of a piston of the loading hydraulic cylinder meets the formulaD 2 -d 2 = d 2 Wherein, the method comprises the steps of, wherein,Drepresenting the large diameter of the piston,drepresenting the diameter of the piston rod.
2. The device of claim 1, wherein the low-pass loading device uses loading force as an output.
3. The device for testing the loading of an aviation actuator in a vibration environment according to claim 1, wherein the hydraulic pump is a quantitative hydraulic pump, and the rated flow rate of the hydraulic pump is more than 60L/min.
4. The device for testing the loading of the aviation actuator in the vibration environment according to claim 3, wherein the proportional relief valve is an electro-hydraulic inverse proportional relief valve, the rated flow is larger than 60L/min, and the response frequency is smaller than 30Hz.
5. The device for testing the loading of the aviation actuator under the vibration environment according to claim 1, wherein the first high-speed switching valve and the second high-speed switching valve are in an on state and an off state when working, the first high-speed switching valve is respectively communicated with a rodless cavity and a rod cavity of the loading hydraulic cylinder, and the second high-speed switching valve is respectively communicated with the rodless cavity of the loading hydraulic cylinder and the pressure oil tank.
6. A loading method using the aeronautical actuator loading test device in a vibration environment according to any one of claims 1 to 5, comprising the steps of:
s1: the second motor and the second hydraulic pump always keep an operating state, and constant oil flow is provided for a rod cavity of the loading hydraulic cylinder;
s2: when the piston rod of the loading hydraulic cylinder stretches out, the loading hydraulic cylinder stretches out leftwards under the drive of the tested actuator, and the loading force direction is rightwards;
s3: the first high-speed switch valve Guan Faguan and the second high-speed switch valve are opened, and a rodless cavity of the loading hydraulic cylinder and a pressure oil tank are communicated;
s4: the loading hydraulic cylinder moves leftwards, and oil in the rod cavity flows back to the pressure oil tank through the electro-hydraulic inverse proportion overflow valve;
s5: the pressure oil tank supplements oil to the rodless cavity through the first one-way valve and the second high-speed switch valve;
s6: the control system calculates a theoretical output force instruction according to the signal of the displacement sensor, compares the theoretical output force instruction with the signal of the force sensor, sends a control signal to the electro-hydraulic inverse proportion overflow valve, controls the pressure of a rod cavity of the loading hydraulic cylinder, and realizes the extension of a piston rod;
s7: when the piston rod of the loading hydraulic cylinder is retracted, the loading hydraulic cylinder is retracted rightwards under the drive of the tested actuator, and the direction of loading force is leftwards;
s8: the first high-speed switch valve is opened, a rod cavity and a rodless cavity of the loading hydraulic cylinder are communicated, and the second high-speed switch valve is closed;
s9: the loading hydraulic cylinder moves rightwards, and the oil in the rodless cavity supplements oil to the rod-containing cavity through the first high-speed switch valve and the second one-way valve;
s10: the redundant oil in the rod cavity flows back to the pressure oil tank through the electro-hydraulic inverse proportion overflow valve;
s11: the control system calculates a theoretical output force command according to the signal of the displacement sensor, compares the theoretical output force command with the signal of the force sensor, sends a control signal to the electro-hydraulic inverse proportion overflow valve, controls the pressure of the rod cavity of the loading hydraulic cylinder, and realizes the retraction of the piston rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910167580.6A CN109696308B (en) | 2019-03-06 | 2019-03-06 | Aviation actuator loading test device under vibration environment and loading method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910167580.6A CN109696308B (en) | 2019-03-06 | 2019-03-06 | Aviation actuator loading test device under vibration environment and loading method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109696308A CN109696308A (en) | 2019-04-30 |
| CN109696308B true CN109696308B (en) | 2023-09-15 |
Family
ID=66235104
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910167580.6A Active CN109696308B (en) | 2019-03-06 | 2019-03-06 | Aviation actuator loading test device under vibration environment and loading method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109696308B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110160718B (en) * | 2019-05-21 | 2021-01-05 | 北京强度环境研究所 | Anti yawing force capability test device of pneumatic cylinder |
| CN112179596B (en) * | 2020-09-25 | 2022-07-29 | 中国直升机设计研究所 | Durability test method and device for vibration active control actuator |
| CN113933173B (en) * | 2021-11-22 | 2023-06-20 | 中国船舶科学研究中心 | Device and method for testing structure of polar region low-temperature environment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596752A (en) * | 2015-01-20 | 2015-05-06 | 中国矿业大学 | Six-degree of freedom parallel mechanism loading system and method |
| CN105673621A (en) * | 2016-03-01 | 2016-06-15 | 浙江大学 | Multi-working-condition comprehensive simulation test system for reciprocating seal of aviation actuator |
| CN107014674A (en) * | 2017-06-12 | 2017-08-04 | 福建工程学院 | The loading device and loading method of Geotechnical Engineering model test |
| WO2018041257A1 (en) * | 2016-09-05 | 2018-03-08 | 安徽理工大学 | Hydraulic system of device for testing comprehensive performance of high-pressure gear flowmeter and testing method |
-
2019
- 2019-03-06 CN CN201910167580.6A patent/CN109696308B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596752A (en) * | 2015-01-20 | 2015-05-06 | 中国矿业大学 | Six-degree of freedom parallel mechanism loading system and method |
| CN105673621A (en) * | 2016-03-01 | 2016-06-15 | 浙江大学 | Multi-working-condition comprehensive simulation test system for reciprocating seal of aviation actuator |
| WO2018041257A1 (en) * | 2016-09-05 | 2018-03-08 | 安徽理工大学 | Hydraulic system of device for testing comprehensive performance of high-pressure gear flowmeter and testing method |
| CN107014674A (en) * | 2017-06-12 | 2017-08-04 | 福建工程学院 | The loading device and loading method of Geotechnical Engineering model test |
Non-Patent Citations (1)
| Title |
|---|
| 张哲 ; 聂扬 ; 滕明.振动环境下航空作动器加载试验的研究.《航空标准化与质量》.2019,全文. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109696308A (en) | 2019-04-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109696308B (en) | Aviation actuator loading test device under vibration environment and loading method thereof | |
| CN103644151B (en) | The test bed hydraulic control system of energy-conservation low impact hydraulic cylinder | |
| CN105003494B (en) | A kind of actuator | |
| CN101852220B (en) | Controllable high-pressure high-flow generating device and control method thereof | |
| CN103775437B (en) | Cylinder bench load simulating device and controlling method thereof | |
| CN106168535B (en) | A kind of fatigue load experimental rig of leaf springs of car | |
| CN103775442B (en) | Hydraulic cylinder test bed pump control Power Recovery hydraulic control system | |
| CN102705302A (en) | Dynamic testing system for high-pressure large-flow oil cylinder | |
| CN103148032B (en) | A kind of Study of Cyclic Loading hydraulic system | |
| CN105547859A (en) | Experiment device and method for simulating situation that natural gas pipeline bears vibration and bending moment load | |
| CN102269235B (en) | Magneto-rheological fluid (MRF) damper based pressure fluctuation self-adjusting system and adjusting method | |
| CN104535243A (en) | Reciprocating seal experiment table for measuring friction feature of single seal ring | |
| CN104006034A (en) | Hydraulic servo variable-load loading test bench | |
| CN103148033B (en) | A kind of Study of Cyclic Loading hydraulic system | |
| CN104948540A (en) | Load simulation electro-hydraulic servo control device for beam-pumping unit | |
| CN106323776A (en) | Fatigue testing device of damping pad | |
| CN103196667A (en) | Electromagnetism energizing connecting rod fatigue test bed | |
| RU191471U1 (en) | Aircraft dynamical load testing machine | |
| CN113417906A (en) | Long-stroke hydraulic cylinder reliability test device for cantilever crane machinery | |
| CN209387276U (en) | Aviation actuator load testing machine under vibration environment | |
| CN204851866U (en) | Beam -pumping unit load simulation electricity liquid servo control device | |
| CN110470501B (en) | Mechanical multipoint synchronous loading device | |
| CN107271288B (en) | 10,000 tons load testing machine moving beam lifting system | |
| CN209800428U (en) | Crank connecting rod double-cylinder hydraulic high-frequency high-voltage pulse impact test device | |
| CN202031898U (en) | Heating furnace walking beam elevation hydraulic control device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |